Mobile vane for a turbine engine, comprising a lug engaging in a locking notch of a rotor disk

Patent metadata

Field	Value
Publication number	US-2017226875-A1
Application number	US-201515515195-A
Country	US
Kind code	A1
Filing date	Sep 28, 2015
Priority date	Sep 30, 2014
Publication date	Aug 10, 2017
Grant date	—

Abstract

A mobile vane for a turbine engine, including a root designed to be inserted into a receiving element of a rotor disk for a turbine engine, a platform carried by the root, and a blade extending from the platform. The platform includes an upstream edge. The upstream edge includes a lug for engaging in a locking notch of the disk in such a way as to hold the vane axially in relation to the disk, according to the longitudinal direction of the receiving element.

First claim

1 - 9 . (canceled)

10 . A mobile vane of a turbomachine, comprising:
a root configured to be inserted in a housing of a rotor disk for a turbomachine, a platform carried by the root, the platform comprising an upstream rim, a blade extending from the platform, wherein the upstream rim comprises a lug for engaging a locking notch of the disk, so as to retain the vane relative to the disk axially downstream along the longitudinal direction of the housing.

11 . A disk for a compressor or turbine of a turbomachine, the disk comprising a housing in which a root of a vane according to claim 10 is configured to be inserted,
wherein the disk comprises at least one locking notch for being engaged with the lug, so as to retain the vane relative to the disk axially downstream along the longitudinal direction of the housing.

12 . The disk according to claim 11 , wherein the longitudinal direction is substantially orthogonal to the radial direction of the disk.

13 . The disk according to claim 11 , wherein the longitudinal direction is substantially orthogonal to a circumferential direction of the disk.

14 . The disk according to claim 11 , wherein the locking notch is a groove substantially extending along the circumferential direction of the disk.

15 . The disk according to claim 11 , wherein the housing extends between two consecutive teeth of the disk, the locking notch being located on only one of both teeth.

16 . A rotor wheel comprising a disk according to claim 11 , such that the platform presses against only one tooth and that the lug engages the locking notch of the tooth.

17 . A turbomachine module chosen from a turbine and a compressor, the module comprising a rotor wheel according to claim 16 .

18 . A turbomachine comprising a module according to claim 17 .

Assignees

• Safran Aircraft Engines

Inventors

• Desforges Jean-Baptise Vincent
• Quelven Damien Bernard
• Judet Maurice Guy
• Tang Ba-Phuc

Classifications

• F01D5/326

  Locking of axial insertion type blades by other means · CPC title

• F01D5/3007 Primary

  of axial insertion type · CPC title

• F01D11/006

  Sealing the gap between rotor blades or blades and rotor · CPC title

• F01D11/00

  Preventing or minimising internal leakage of working-fluid, e.g. between stages (sealings in general F16J {; sealing arrangements for transition ducts of combustor cans F01D9/023}) · CPC title

• F01D5/32

  Locking, e.g. by final locking blades or keys · CPC title